| 高超声速自适应激波针数值研究 |
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| 引用本文： | 耿云飞,阎超. 高超声速自适应激波针数值研究[J]. 力学学报, 2011, 43(3): 441-446. DOI: 10.6052/0459-1879-2011-3-lxxb2010-732 |
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| 作者姓名： | 耿云飞 阎超 |
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| 作者单位： | 北京航空航天大学 国家计算流体力学实验室 |
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| 基金项目： | 国家自然科学基金资助项目(90716010)~~ |
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| 摘 要： | 针对传统的与钝体轴线共线安装的固定式激波针方法在有攻角状态所存在的问题, 在前人工作基础上得到一种新型高超声速飞行器减阻/降热方法------自适应激波针方法. 将该方法应用于三维高超声速轴对称钝锥外形以及扁平楔外形, 并采用数值模拟的方法对其进行了概念验证. 在0○~120○攻角范围内, 对不同L/D参数的激波针外形流场以及前缘壁面的压力、热流分布等进行了对比分析. 结果表明, 这种新型自适应激波针方法无论在无攻角还是有攻角状态, 均可有效降低高超声速飞行器头部壁面的压力和热流, 可以有效解决传统激波针方法在较大攻角情况状态下失效的问题.
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| 关 键 词： | 数值模拟 |
| 收稿时间： | 2010-11-03 |
| 修稿时间： | 2010-12-20 |
NUMERICAL INVESTIGATION OF SELF-ALIGNING SPIKED BODIES AT HYPERSONIC SPEEDS |
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| Geng Yunfei , Yan Chao. NUMERICAL INVESTIGATION OF SELF-ALIGNING SPIKED BODIES AT HYPERSONIC SPEEDS[J]. chinese journal of theoretical and applied mechanics, 2011, 43(3): 441-446. DOI: 10.6052/0459-1879-2011-3-lxxb2010-732 |
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| Authors: | Geng Yunfei Yan Chao |
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| Affiliation: | National Laboratory for Computational Fluid Dynamics, Beihang University, Beijing 100191, China |
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| Abstract: | The conventional fixed spike method,in which the spike is mounted with an alignment along the body-axis,always failed at relatively high angles of attack;therefore,a new self-aligning spike method is investigated in the present paper.This method is applied to 3D axi-symmetrical blunt cone and compressed wedge configurations at hypersonic speeds.Numerical simulations are carried out to verify this new concept. Spiked geometries with different L/D parameters at angle of attack ranged from 0 to 12 degrees are ... |
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| Keywords: | hypersonic drag reduction heat flux aerospike numerical simulation |
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